E ASA AD No.: 20 1 4

- 0141

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 1 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. 

## EASA AIRWORTHINESS DIRECTIVE

AD No

. : 20 1 4

- 0141

Date: 04 June 2014

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation.
This AD is issued in accordance with EU 748/2012, Part 21.A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may ope rate an aircraft to which an AD applies, except in accordance with the requ irements of that AD, unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]

. 

### Design Approval Holder’s Name: AIRBUS Type/Model designation(s): A318, A319 and A320 aeroplanes

TCDS Number: EASA.A.064

F oreign AD: Not applicable

Supersedure: None



### ATA 3 2 Landing Gear

– Main Landing Gear Upper Cardan

– Life Limitation

Manufacturer: Airbus (formerly Airbus Industrie)

Applicability: Airbus A318

- 111, A318

- 112, A318

- 121, A318

- 122, A319

- 111, A319

- 112, A319

- 113, A319

- 114, A319

- 115, A319

- 131, A319

- 132, A319

- 133, A320

- 211, A320

- 212, A320

- 214, A320

- 215, A320

- 216, A320

- 231, A320

- 232 and A320

- 233 aeroplanes , all manufacturer serial numbers

.
Reason: During an A320

- 200 77 T m ain l anding g ear (MLG) fatigue test by Messier Bugatti

- Dowty (MBD), an u pper c ardan was found with a crack
, emanating from the grea se hole / main lug intersection. The affected u pper c ardan , Part Number (P/N) 201163620, is listed in the applicable Airworthiness Limitations Section (ALS) Part 1 with a demonstrated fatigue life of 60 000 l anding s

. This condition, if not corrected
, could lead to MLG u pper c ardan f ailure
, possibly resulting in MLG collapse and subsequent damage to the aeroplane and injury to occupants

. Prompted by these findings and further to analysis , it has been decided to reduce th e life limit for certain installation s of the P/N 201163620 MLG u pper c ardan

. For the reasons described above, this AD requires implementation of the new life limit s , as applicable, and replacement of any affected MLG u pper c ardan unit s that have already exceeded the reduced limit.
The reduced life limits for the affected MLG u pper c ardan are expected to be incorporated in a next revision of the Airbus A318/A319/ A320 /A321 ALS Part 1

.
Effective Date: 18 June 2014E ASA AD No.: 20 1 4

- 0141

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 2 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet. Required A ction(s) and Compliance Time(s) : Required as indicated, unless accomplished previously: (1) Within 3 months after the effective date of this AD
, or before exceeding the life limit as defined in Appendix 1 of this AD, as applicable, whichever occurs later, replace each MLG upper cardan P/N 201163620 with a serviceable part.
Note 1 : For the purpose of this AD, a serviceable MLG u pper c ardan is a part having P/N 201163620 that has not exceeded the life limit defined in Appendix 1 of this AD , or a MLG u pper c ardan having a different P/N that has not exceeded the life limit defined in Airbus A318 / A319 / A320 / A321 ALS Part 1 Revision 02

. (2) From the effective date of this AD, it is allowed to install a MLG u pper c ardan P/N 201163620 on an aeroplane, provided the part life has not exceeded the life limit defined in Appendix 1 of this AD
, as applicable, and that, following installation, it is replaced before exceeding the applicable life limit as defined in Appendix 1 of this AD (see Notes 4 and 6 ) with a serviceable part (see Note 1 above)

.
Ref. Public ations: Airbus A318/A319/ A320 /A321 ALS Part 1 R evision 02, dated 13 May 2011. The use of later approved revisions of this document is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD.
2. This AD was posted on 25 March 2014 as PAD 14

- 057 for consultation until 08 April 2014. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Safety Information Section, Executive Directorate, EASA. E

- mail: ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in t his AD, please contact: AIRBUS

– Airworthiness Office

– EIAS, Fax +33 5 61 93 44 51, E

- mail: account.airworth

- eas@airbus.com

.E ASA AD No.: 20 1 4

- 0141

TE. CAP.0011 0

- 00 3 © European Aviation Safety Agency. All rights reserved. 3 / 3 Proprietary document. Copies are not controlled. Confirm revision status through the EASA

- Internet/Intranet.



### Appendix 1

– MLG U pper C ardan P/N 201163620 L ife L imit

Note 2 : The life limit as specified in this Appendix (see table below) is counted in landings, accumulated

by the MLG unit since its first installation on an aeroplane.
Note 3 : T he life limit applies only whe re the installation is valid for the given aeroplane model
,

configuration, and weight variant (WV)

. Note 4 : In case of transfer of a part between aeroplanes having a different life limitation, refer to the

Airbus A318 / A319 / A320 / A321 ALS Part 1 R evision 02 sub

- part 1

- 0 paragraph 6 for the method to adjust the life limitation.
Note 5 : A MLG unit on which Airbus modification ( mod ) 26644 is embodied (i.e. post

- mod) is also

known as “Enhanced” landing gear. Pre

- mod 26644 MLG unit s are identified as P/N 201375xxx Leg and Dressing Series and p ost

- mod 26644 MLG unit s are identified as P/N 201582xxx Leg and Dressing ser ies.
Note 6 : For aeroplanes and configurations not defined in the table below, the life limitation is unchanged

and th os e as specified in Airbus A318/A319/A320/A321 ALS Part 1 at R evision 02 still apply.
Note 7: C ertain life limits were stated incorrectly in PAD 14

- 057, as 50 950 FC instead of 50 590 FC

.

The Table below shows the correct values.



### Affected aeroplanes Life Limit (see Note 2 above )

A319 p re
- m od 26644
, excluding Corporate Jets post

- mod 28238, 28162 and 28342 50 5 90
A319 post

- m od 26644
, excluding Corporate Jets post

- mod 28238, 28162 and 28342 56 480

A320 Twin pre
- m od 26644
, WV 012, WV011, WV016 and WV018 50 5 90

A320 Twin p ost

- m od 26644
, WV012, WV011, WV016 and WV018 56 480
A320 Twin post

- mod 26644
, WV015 and WV017 42 140